Aircraft bleed air auxiliary test equipment

Abstract

The utility model discloses an aircraft bleed air auxiliary test device, and relates to the technical field of aviation aircraft valve test and maintenance, the aircraft bleed air auxiliary test device comprises a test cabin and a test bench, the middle part of the upper surface of the test bench is provided with an aircraft valve through a tool module, and two ends of the aircraft valve are respectively provided with an air inlet adapter and an air outlet adapter; a first valve connector is arranged at the other end of the aircraft valve, and a second valve connector is further arranged at the position, close to the middle, of the aircraft valve. According to the design, the rapid clamping and replacing efficiency of the aircraft valve can be improved, various valves are connected in series / in parallel, different valves can be opened and closed according to different testing requirements, switching of testing pipelines is achieved, the testing efficiency is improved, the testing cost is reduced, and the testing efficiency is improved. The multi-purpose machine is achieved, full-intelligent data collection is adopted, all parameters such as pressure and flow can be fed back to an external operation computer in real time, and real-time checking is facilitated.

Description

Technical Field

[0001] This utility model relates to the field of testing and maintenance technology for aircraft valves, and in particular to an aircraft bleed air auxiliary testing device. Background Technology

[0002] Testing and maintaining aircraft valves is a critical task in ensuring the safe operation of aircraft. Valves (also known as airlocks) are primarily used in aircraft to control airflow, fluid flow, and system pressure. They are widely used in various aspects of aircraft systems, including fuel systems, hydraulic systems, air conditioning systems, engine cooling systems, and emergency pressure relief systems. To ensure aircraft safety and performance, valves must always function optimally, which necessitates regular testing and maintenance.

[0003] Existing bleed air system valve maintenance and testing require specialized equipment recommended by component manufacturers or the use of a corresponding aircraft engine as a test platform. This involves frequent disassembly and a large workload, long equipment start-up time, and high energy consumption. Therefore, this utility model provides an aircraft bleed air auxiliary tooling and testing equipment. Utility Model Content

[0004] To address the shortcomings of existing technologies, this utility model provides an aircraft bleed air auxiliary tooling and testing equipment, which solves the problems mentioned in the background.

[0005] To achieve the above objectives, this utility model is implemented through the following technical solution: an aircraft bleed air testing device, including a test chamber, a test platform is installed inside the test chamber, and positioning legs are provided at the four corners of the test platform, and the test platform is fixed inside the test chamber by the positioning legs;

[0006] An aircraft valve is provided in the middle of the upper surface of the test bench. An air intake adapter and an exhaust adapter are provided at both ends of the aircraft valve, and a valve interface one is provided at the other end of the aircraft valve. A valve interface two is also provided near the middle of the aircraft valve.

[0007] The test bench is equipped with a third intake pipe connected to the intake adapter, a third exhaust pipe connected to the exhaust adapter, a first intake pipe connected to valve interface one, and a second intake pipe connected to valve interface two. The first intake pipe, the second intake pipe, the third intake pipe, and the third exhaust pipe are all installed on the test bench.

[0008] As a further technical solution of this utility model, the first intake pipe is equipped with a regulator, a toggle valve, and a pressure gauge. The first intake pipe is also branched into a first exhaust pipe and a first branch pipe. The first exhaust pipe is equipped with a toggle valve, and the first branch pipe is equipped with a toggle valve and a reducing diameter connecting pipe. The other end of the first branch pipe is connected to the third intake pipe.

[0009] As a further technical solution of this utility model, the second intake pipe is equipped with a regulator, a pressure gauge, a shut-off valve, and a shut-off valve. One end of the second intake pipe is connected to the valve interface and the second branch pipe through a three-way pipe. The second intake pipe is also connected to the third intake pipe through the shut-off valve and the pipe.

[0010] As a further technical solution of this utility model, the second branch pipe is connected to the third exhaust pipe, and the second branch pipe is also provided with a shut-off valve three, a shut-off valve four and a metering valve. The second branch pipe is also connected to the second exhaust pipe through the metering valve.

[0011] As a further technical solution of this utility model, the third air intake pipe is equipped with a system airflow measuring instrument, a regulator three, a shut-off valve five and a pressure gauge three, the third exhaust pipe is equipped with a pressure gauge four and a shut-off valve six, and the third air intake pipe and the third exhaust pipe are connected by an aircraft valve.

[0012] As a further technical solution of this utility model, it also includes a left and right sliding door on the side of the test chamber corresponding to the test platform, an adjustable operating computer on the outer side of the test chamber, a printer rack installed on the outer side of the test chamber near the operating computer, and a power distribution cabinet on the outer side of the test chamber.

[0013] An aircraft bleed air auxiliary tooling includes a tooling module installed between a test bench and an aircraft valve for quick replacement and fixation of the aircraft valve.

[0014] The tooling module includes a base mounted on the upper surface of the test bench. Two slide rails are symmetrically mounted on the base. Two lower brackets are slidably connected to the two slide rails. Each lower bracket is hinged to an upper bracket. One end of the upper bracket is hinged to the lower bracket, and the other end of the upper bracket and the lower bracket are fixed by bolts. The inner sides of the upper bracket and the lower bracket are provided with slots. The aircraft valve is fixed to the test bench by the tooling module.

[0015] As a further technical solution of this utility model, the upper surface of the slide rail is provided with a plurality of positioning holes at equal intervals, and the bottom end of the lower card seat is provided with a through hole corresponding to the positioning holes.

[0016] This utility model provides an auxiliary tooling and testing equipment for aircraft bleed air, which has the following advantages compared with the prior art:

[0017] 1. This design adopts a quick-change test fixture module and uses quick-release clamps for clamping. Compared with the existing test technology for aircraft engine testing, it can reserve more space for the installation position of aircraft valves, further improving the efficiency of quick clamping and replacement of aircraft valves. At the same time, the transparent explosion-proof glass window makes it easier to observe the operation status of aircraft valves.

[0018] 2. This design uses multiple valves in series / parallel, allowing different valves to be switched according to different test requirements, enabling the switching of test pipelines and achieving multi-purpose functionality. Moreover, it uses high-pressure compressed air as the air source, which consumes less energy and starts up faster compared to existing aircraft engine testing technologies. Furthermore, it adopts fully intelligent data acquisition, and various parameters such as pressure and flow rate can be fed back to the external operating computer in real time for convenient real-time viewing. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the structure of an aircraft bleed air testing device.

[0020] Figure 2 This is a schematic diagram of the installation of an aircraft valve in an aircraft bleed air testing device.

[0021] Figure 3 A top view of an aircraft valve and tooling module in an aircraft bleed air auxiliary tooling;

[0022] Figure 4 This is a schematic diagram of the structure of an aircraft valve and tooling module in an aircraft bleed air auxiliary tooling.

[0023] Figure 5 This is a schematic diagram illustrating the working principle of an aircraft bleed air testing device.

[0024] In the diagram: 1. Test chamber; 11. Operating computer; 12. Power distribution cabinet; 13. Printer rack; 14. Left and right sliding doors; 2. Test platform; 21. Positioning support legs;

[0025] 3. Aircraft valve; 31. Intake adapter; 32. Exhaust adapter; 33. Valve interface one; 34. Valve interface two;

[0026] 4. Tooling module; 40. Base; 41. Upper bracket; 42. Lower bracket; 43. Slide rail; 44. Positioning hole;

[0027] 5. First intake pipe; 51. Regulator 1; 52. Actuating valve 1; 53. Pressure gauge 1; 54. First exhaust pipe; 55. Actuating valve 2; 56. First branch pipe; 57. Actuating valve 3; 58. Reduced diameter connecting pipe;

[0028] 6. Second intake pipe; 61. Regulator II; 62. Pressure gauge II; 63. Shut-off valve I; 64. Shut-off valve II; 65. Second branch pipe; 66. Shut-off valve III; 67. Shut-off valve IV; 68. Metering valve;

[0029] 7. Third intake pipe; 71. System airflow measuring instrument; 72. Regulator three; 73. Shut-off valve five; 74. Pressure gauge three; 75. Third exhaust pipe; 76. Pressure gauge four; 77. Shut-off valve six. Detailed Implementation

[0030] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model without creative effort are within the protection scope of the present utility model.

[0031] Please see Figure 1 As shown, this utility model provides a technical solution for aircraft bleed air auxiliary tooling and testing equipment: an aircraft bleed air testing device, including a test chamber 1, a test platform 2 installed inside the test chamber 1, and positioning legs 21 set at each of the four corners of the test platform 2. The test platform 2 is fixed inside the test chamber 1 by the positioning legs 21. It also includes left and right sliding doors 14 set on the side of the test chamber 1 corresponding to the test platform 2. The left and right sliding doors 14 are equipped with transparent explosion-proof glass windows to facilitate observation of the operation status of the aircraft valve 3. An adjustable operating computer 11 is also set on the outer side of the test chamber 1, and a printer rack 13 is installed on the outer side of the test chamber 1 near the operating computer 11. A printer can be placed on the printer rack 13 to facilitate connection with the operating computer 11 for printing test data. A power distribution cabinet 12 is set on the outer side of the test chamber 1 to supply power to the testing equipment.

[0032] like Figure 2 and 3 As shown, an aircraft valve 3 is provided in the middle of the upper surface of the test bench 2. An air intake adapter 31 and an exhaust adapter 32 are provided at both ends of the aircraft valve 3, and a valve interface 1 33 is provided at the other end of the aircraft valve 3. A valve interface 2 34 is also provided near the middle of the aircraft valve 3. The test bench 2 is equipped with a third air intake pipe 7 connected to the air intake adapter 31, a third exhaust pipe 75 connected to the exhaust adapter 32, a first air intake pipe 5 connected to the valve interface 1 33, and a second air intake pipe 6 connected to the valve interface 2 34. The first air intake pipe 5, the second air intake pipe 6, the third air intake pipe 7, and the third exhaust pipe 75 are all provided on the test bench 2.

[0033] (1) When testing the simulated aircraft signal tube section, refer to Figure 5 The thick black pipeline section in the middle is for simulating the pressure of the control pipeline;

[0034] The first intake pipe 5 is equipped with a regulator 51, a toggle valve 52 and a pressure gauge 53. The first intake pipe 5 is also branched into a first exhaust pipe 54 and a first branch pipe 56. The first exhaust pipe 54 is equipped with a toggle valve 55, and the first branch pipe 56 is equipped with a toggle valve 57 and a reducing diameter connecting pipe 58. The other end of the first branch pipe 56 is connected to the third intake pipe 7.

[0035] During testing, the aircraft needs to control the valves pneumatically through the upstream and downstream pressures of the aircraft valve 3. Therefore, a reference pressure is required. High-pressure compressed air is provided by a high-pressure air pump as the air source and enters the test equipment from the first air intake pipe 5. The intake pressure is initially adjusted by the regulator 51 and enters the toggle valve 52 as the main switch valve for entering the equipment. The intake pressure can be viewed by the pressure gauge 53. The toggle valve 55 can be used as the exhaust switch of the intake pipe for airflow bypass before or after the test ends.

[0036] Furthermore, the airflow will be divided into two parts. One part connects to the valve interface 33 of the aircraft valve 3 to realize the signal tube connection of the aircraft valve 3, so as to simulate the aircraft to provide a reference pressure. The other part opens and closes the airflow through the toggle valve 57, and then converges the airflow and increases the flow rate through the reduced diameter connecting pipe 58, finally reaching the airflow inlet of the valve (i.e., on the third air intake pipe 7). In conjunction with the regulator 72, the minimum opening pressure test of the aircraft valve 3 is performed. It should be noted that the reduced diameter connecting pipe 58 is a pipe with a smaller inner diameter than the inner diameter of the first branch pipe 56. The purpose is to converge the airflow and increase the flow rate.

[0037] (2) When testing for leakage of aircraft valve 3, refer to Figure 5 The black thin tubing section is a diagram illustrating a leak test of aircraft valve 3.

[0038] The second intake pipe 6 is equipped with a regulator 2 61, a pressure gauge 2 62, a shut-off valve 1 63, and a shut-off valve 2 64. One end of the second intake pipe 6 is connected to the valve interface 2 34 and the second branch pipe 65 through a three-way pipe. The second intake pipe 6 is also connected to the third intake pipe 7 through the shut-off valve 2 64 and a pipe. The second branch pipe 65 is connected to the third exhaust pipe 75. The second branch pipe 65 is also equipped with a shut-off valve 3 66, a shut-off valve 4 67, and a metering valve 68. The second branch pipe 65 is also connected to the second exhaust pipe through the metering valve 68.

[0039] During the test, the aircraft valve 3 under test is a rotary valve, which allows a certain amount of airflow leakage.

[0040] High-pressure compressed air is provided by a high-pressure air pump as the air source and enters the test equipment through the second air inlet pipe 6. The pressure of the inlet pipe is regulated by regulator 2 61 and indicated at pressure gauge 2 62. Shut-off valve 1 63 switches the airflow into the test equipment. Shut-off valve 2 64 controls the airflow entering the test aircraft valve 3 in the forward direction. Shut-off valve 3 66 controls the airflow entering the test aircraft valve 3 in the reverse direction. Shut-off valve 4 67 controls the exhaust to maintain the test pressure. Metering valve 68 can measure the amount of leakage exhaust.

[0041] (3) When the simulated aircraft is supplied with air, refer to Figure 5 The thick gray pipeline section is a simulated gas supply section;

[0042] The third intake pipe 7 is equipped with a system airflow measuring instrument 71, a regulator 72, a shut-off valve 73, and a pressure gauge 74. The third exhaust pipe 75 is equipped with a pressure gauge 76 and a shut-off valve 77. The third intake pipe 7 and the third exhaust pipe 75 are connected by an aircraft valve 3.

[0043] Because aircraft need to draw air from their engines to supply downstream users, during specific testing:

[0044] High-pressure compressed air is provided by a high-pressure air pump as the air source and enters the test equipment through the third air inlet pipe 7. The airflow into the equipment is regulated and displayed by the system airflow measuring instrument 71. The pressure is controlled by the regulator 3 72. The shut-off valve 5 73 can be used as the switch control for the airflow entering the test aircraft valve 3. The pressure before entering the test aircraft valve 3 is indicated by the pressure gauge 3 74. After entering the test aircraft valve 3, the airflow passes through the pressure gauge 4 76 to display the outlet pressure. The shut-off valve 6 77 can be used to close the exhaust and is used for leakage testing.

[0045] like Figure 2-4As shown, an aircraft bleed air auxiliary tooling includes a tooling module 4 installed between a test bench 2 and an aircraft valve 3 for quick replacement and fixation of the aircraft valve 3. The tooling module 4 includes a base 40 installed on the upper surface of the test bench 2. Two slide rails 43 are symmetrically installed on the base 40. Two lower retainers 42 are slidably connected to the two slide rails 43. Each lower retainer 42 is hinged to an upper retainer 41. One end of the upper retainer 41 is hinged to one end of the lower retainer 42, and the other end of the upper retainer 41 is hinged to the other end of the lower retainer 42. The upper and lower brackets 41 and 42 are fixed with bolts. The inner sides of the upper bracket 41 and the lower bracket 42 are provided with slots. The aircraft valve 3 is fixed on the test bench 2 by the tooling module 4. Before the test, the aircraft valve 3 is placed on the two lower brackets 42 and the lower brackets 42 are used to support and position the two ends of the aircraft valve 3. Then the upper bracket 41 is clamped on the lower bracket 42 and one end is fixed with bolts, thereby completing the clamping and positioning of the aircraft valve 3 by the upper bracket 41, which facilitates the subsequent connection of the aircraft valve 3 to the test pipeline.

[0046] The upper surface of the slide rail 43 is provided with multiple positioning holes 44 at equal intervals. The bottom end of the lower bracket 42 is provided with a through hole corresponding to the positioning hole 44. The through hole on the lower bracket 42 and the positioning hole 44 on the slide rail 43 make it convenient to control the distance between the two lower brackets 42 according to the size of the aircraft valve 3. After adjustment, the pin is inserted into the positioning hole 44 through the through hole to adjust and fix the distance between the two lower brackets 42.

[0047] This technology uses a quick-change test tooling module 4, which is clamped using quick-install clamps (i.e., upper clamp 41 and lower clamp 42). Compared with the existing test technology for aircraft engine testing, it can reserve more space for the installation position of the aircraft valve 3. At the same time, the transparent explosion-proof glass window makes it easier to observe the operation status of the aircraft valve 3.

[0048] The above description is merely a preferred embodiment of this utility model. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of this utility model, and these improvements and modifications should also be considered within the scope of protection of this utility model. Structures, devices, and operating methods not specifically described or explained in this utility model are implemented according to conventional methods in the art, unless otherwise specified or limited.

Claims

1. An aircraft bleed air assisted test apparatus, characterized by, The test chamber (1) and the aircraft air bleed auxiliary tooling are included. The test chamber (1) is equipped with a test platform (2), and the test platform (2) is provided with positioning legs (21) at the four corners. The test platform (2) is fixed inside the test chamber (1) by the positioning legs (21). The test bench (2) has an aircraft valve (3) in the middle of its upper surface. The two ends of the aircraft valve (3) are respectively provided with an air intake adapter (31) and an exhaust adapter (32). The other end of the aircraft valve (3) is provided with a valve interface one (33). The aircraft valve (3) is also provided with a valve interface two (34) near the middle. The test bench (2) is equipped with a third intake pipe (7) connected to the intake adapter (31), a third exhaust pipe (75) connected to the exhaust adapter (32), a first intake pipe (5) connected to valve interface one (33), and a second intake pipe (6) connected to valve interface two (34). The first intake pipe (5), the second intake pipe (6), the third intake pipe (7) and the third exhaust pipe (75) are all set on the test bench (2).

2. An aircraft bleed air assisted test apparatus as claimed in claim 1, wherein, The first intake pipe (5) is equipped with a regulator (51), a toggle valve (52) and a pressure gauge (53). The first intake pipe (5) is also branched into a first exhaust pipe (54) and a first branch pipe (56). The first exhaust pipe (54) is equipped with a toggle valve (55). The first branch pipe (56) is equipped with a toggle valve (57) and a reduced diameter connecting pipe (58). The other end of the first branch pipe (56) is connected to the third intake pipe (7).

3. An aircraft bleed air assisted test apparatus as defined in claim 1, wherein, The second intake pipe (6) is equipped with regulator two (61), pressure gauge two (62), shut-off valve one (63) and shut-off valve two (64). One end of the second intake pipe (6) is connected to valve interface two (34) and second branch pipe (65) through a three-way pipe. The second intake pipe (6) is also connected to the third intake pipe (7) through shut-off valve two (64) and pipe.

4. An aircraft bleed air assisted test apparatus as claimed in claim 3, wherein, The second branch pipe (65) is connected to the third exhaust pipe (75), and the second branch pipe (65) is also equipped with a shut-off valve three (66), a shut-off valve four (67) and a metering valve (68). The second branch pipe (65) is also connected to the second exhaust pipe through the metering valve (68).

5. An aircraft bleed air assisted test apparatus as defined in claim 1, wherein, The third intake pipe (7) is equipped with a system airflow measuring instrument (71), regulator three (72), shut-off valve five (73) and pressure gauge three (74), and the third exhaust pipe (75) is equipped with pressure gauge four (76) and shut-off valve six (77). The third intake pipe (7) and the third exhaust pipe (75) are connected by an aircraft valve (3).

6. An aircraft bleed air assisted test apparatus as defined in claim 1, wherein, It also includes a left and right sliding door (14) on the side of the test chamber (1) corresponding to the test platform (2), an adjustable operating computer (11) on the outer side of the test chamber (1), a printer rack (13) installed on the outer side of the test chamber (1) near the operating computer (11), and a power distribution cabinet (12) on the outer side of the test chamber (1).

7. An aircraft bleed air assisted test apparatus as defined in claim 1, wherein, The aircraft bleed air auxiliary tooling includes a tooling module (4) installed between the test bench (2) and the aircraft valve (3) for quick replacement and fixing of the aircraft valve (3). The tooling module (4) includes a base (40) mounted on the upper surface of the test bench (2). Two slide rails (43) are symmetrically mounted on the base (40). Two lower brackets (42) are slidably connected on the two slide rails (43). Each lower bracket (42) is hinged to an upper bracket (41). One end of the upper bracket (41) is hinged to the lower bracket (42), and the other end of the upper bracket (41) and the lower bracket (42) are fixed by bolts. The inner sides of the upper bracket (41) and the lower bracket (42) are provided with slots. The aircraft valve (3) is fixed on the test bench (2) by the tooling module (4).

8. An aircraft bleed air assisted test apparatus as claimed in claim 7, wherein, The upper surface of the slide rail (43) is provided with a plurality of positioning holes (44) at equal intervals, and the bottom end of the lower card holder (42) is provided with a through hole corresponding to the positioning holes (44).

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